NDLI: Comparison of wind tunnel test results at free stream mach 0.7 with results from the boeing tea-230 subsonic flow method. [wing flow method tests

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Comparison of wind tunnel test results at free stream mach 0.7 with results from the boeing tea-230 subsonic flow method. [wing flow method tests

Content Provider	NASA Technical Reports Server (NTRS)
Author	Mohn, L. W.
Copyright Year	1975
Description	The use of the Boeing TEA-230 Subsonic Flow Analysis method as a primary design tool in the development of cruise overwing nacelle configurations is presented. Surface pressure characteristics at 0.7 Mach number were determined by the TEA-230 method for a selected overwing flow-through nacelle configuration. Results of this analysis show excellent overall agreement with corresponding wind tunnel data. Effects of the presence of the nacelle on the wing pressure field were predicted accurately by the theoretical method. Evidence is provided that differences between theoretical and experimental pressure distributions in the present study would not result in significant discrepancies in the nacelle lines or nacelle drag estimates.
File Size	2360487
Page Count	94
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19750018904
Archival Resource Key	ark:/13960/t5z659f7r
Language	English
Publisher Date	1975-07-01
Access Restriction	Open
Subject Keyword	Aerodynamics Aerodynamic Configurations Swept Wings Subsonic Flow Wing Flow Method Tests Wind Tunnel Stability Tests Nacelles Wind Tunnel Models Potential Flow Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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